sherbondy



E. H. SHERBONDY.

NOZZLE RING. APPLICATION FILED APR. 8. I9I8..

Patented July 22, 1919.

2 SHEETSSHEET lv v w l/VVE/VTOR Ear-Z f2. Sherbonda Z QM/WI ATTORNEY msCOLUMBIA PLANOGRAPH cm, WASHINGTON, D. C.

E. H. SHERBONDY. NOZZLE RING. APPLICATION FILED APR. 8. 191a.

Patented July 22, 1919.

2 SHEETS-SHEET 2- IIVVE/VTOR Ea T-Z .li. flher'bond/a Br 6 ATTORNEY EARLH. SHERBON'DY,OECI1EVELANDK, OHIO.

NOZZLE-RING.

Specification of Letters Patent.

Patented July 22, 1919.

Application filed April 8, 1918. Serial No. 227,331.

This invention relates to a nozzle ring for a turbine and to a method ofmaking same. It is an object of the invention to provide a one piecenozzle ring, having a body portion which serves as means for mountingthe ring as a whole. The nozzle ring in question, is intended andadapted to be used in connection with a gas operated turbine of a typeshown in my co-pending case, Serial No. 224.892, filed March 26, 1918.

Other objects and advantages will appear as the description proceeds.

Referring now to the drawings, in which similar reference charactersindicate similar parts, Figure 1 is a side view partly in section,showing the nozzle ringin position 1n a turbine casing; Fig. 2 is a sideview of the blank at one of the stages of manufacture, Fig. 3 is asectional 'view on an enlarged scale of the same; Fig. 4: is developmentof the edge of the nozzle ring after the slots have been cut; Fig. 5 isa view on line 5-5 of Fig. 4 Fig. 6 is a view similar to Fig. 1 at alater stage of manufacture; Fig. soft alloy, profiling; Fig. 9 is afront view of the finished nozzle ring and Fig. 10 is a view, partly insection and partly in per'spective ofthe same. i

The first stage of the operation of making the one piece nozzle ring, isto take a thickwalled metal tube of a material which will withstand thehigh temperatures met with in a gas operated turbine.

The length ofthis tube may be substantially equal to the line A,B, Fig.3, and the thickness of said tube may be substantially equal to line AD, Fig. 3. The excess metal is then cut away, leaving a comparativelythickend portion 1, the annular portion 2 and an upturned-portion 3; Itshould be mentioned in this connection, that Fig. 3

shows a section through an upper wall of the tube.

The end portion 1 is now undercut as at 1 all the way around, so thataPONY/1011 w1ll overhang this 1 out.

I shows the nozzle ring filled witha Fig. 8 shows the nozzle ring after1 The next stage in making the nozzle ring is to out the slots in theportion 1. These slots designated S, are milled in the edge of the endportion 1 in such a manner that the slots S are helical with respect toa longitudinal axis'ofthe original tube, that is to say, thelongitudinal axis of the annular portion 2. The cutting of these slotsleaves the blades 5 outstanding from the base of the portion 1, it beingevident that the blades 5 will also be helical with respect to the axisof the annular portion 2.

During the said milling operation, the work is fed longitudinally, thatis, in a direction parallel to the axis of the portion 2, a distance AF, equal to the width of the portion 1. At the same time, the workisrotated about the axis of the annular portion 2 an amount equal to thedistance G H, 'Fig. 4; the milling cutter during both of these motions,while itself rotating, does not move otherwise. The resultant of thesetwo motions causes a helical slot to be out, which in the development inFig. 4:, ap pears as a diagonal slot. It should be understood, however,that the body of each slot S, is everywhere equidistant from the axis ofthe portion 2, that is to say, it winds helically around saidaxis.

It will now be apparent that portions 5 of the blades 5, to the right ofthe line 4 4', representing the inner edge of the undercut portion 4,will overhang said undercut portion, as shown in Fig. 5. The-next stagein the making of the nozzle ring is to bend these overhanging portions 5toward the axis of the portion 2, as shown in Fig. 6. The gases areintended to pass through the nozzle ring in a direction shown by thearrows in Fig. 6. The purpose of the justmentioned bending, is to changethe direction of the opening of the slots S, so that the gases that aregoing to operate the turbine will be more readily taken into the slotsS.

This bending operation can be carried out in any desired manner and as amatter of practice, it is accomplished by first heating the portions 5in an oxyacetylene flame to a sufliciently high temperature, thenbending them as shown in a suitable jig. Only the parts 5 of the blades5, overhanging the undercut portion 4, are bent, the purpose of the slot4 being to permit this bending.

The nozzle ring is intended to be located in turbine casing 6, as shownin F ig. 1 and the outer edge of the nozzle ring must be shaped toprovide a proper gas tight seat for the diaphragm 7, located in thecasing 6. The casing 6 carries inlet and exhaust pipes 8 and 9, and thediaphragm 7 is within the casing 6, between these two pipes. The annularportion 2 of the nozzle ring, the diaphragm 7 and the bottom of thecasing 6, together define an inlet chamber 10.

In order to properly profile the blades 5 plete. Holes may be drilled inthe por tion 3 to serve in mounting the whole in the casing 6.

It will thus b seen that I have provided a one piece nozzle ring whichcarries integral therewith, means for supporting it directly on theturbine casing, and which itself serves as a means for seating adiaphragm.

In a structure of this kind, where unusually high temperatures are metwith, it will be evident that it is of distinct advantage to have theblades integral with the body of the ring, because in such a structure,there is no opportunity for erosion, due to the high velocity, hot,exhaust gases causing a weakening of separate connections between thenozzle blades and nozzle ring. The portion 2 may be chamfered at thepoint 18 for clearance purposes.

It should also be noted that the portion 2, serves as a mounting for thenozzle ring and also aids in defining the inlet chamber 10. It shouldalso be noted that the cross-sectional area of the slots S graduallydecreases from right to left of the drawing. This type of nozzlepresents known advantages in turbine nozzle design.

WVhile I have shown one method of making this nozzle ring, it should beunderstood that this method may be modified and that the nozzle ringitself may be modified as defined within the scope of the appendedclaims.

I claim- .1. The method of making a turbine nozzle ring, comprisingcutting away a thick-walled tube to leave an end portion ofsubstantially the thickness of the original tube, and cutting slots insaid end portion helical with respect to the axis of said tube.

The method of making a turbine nozzle ring, comprising cutting away athickwalled tube to leave an end portion of substantial thickness and arelatively thin annular portion, undercutting said end portion, andcuttitng slots in said end portion helical with respect to the axis ofsaid tube.

3. The method of making a turbine nozzle ring, comprising cutting away athick-walled tube'to leave an end portion of substantial thickness and arelatively thin annular portion, undercutting said end portion, andcutting slots in said end portion helical with respectto the axis ofsaid tube, then bending the blades between the slots and adjacent theundercut portion toward the axis of said tube.

4. The method of making a turbine nozzle ring, comprising cutting away athick-walled tube to leave an end portion of substantial thickness and arelatively thin annular portion, undercutting said end portion andcutting slots in said end portion helical with respect to the axis ofsaid tube, then bending the blades between the slots and adj acenttheundercut portion toward the axis of said tube, then filling said slotswith an alloy and turning the outer part of said blades down to aprofile. 1

5. The method of making a turbine nozzle ring, comprising cuttinghelical slots in the periphery of a solid annular blank, said slotsbeing helical with respect to the axis of said ring along the edge ofsaid blank.

6. The method of making a turbine nozzle ring, comprising undercutting asolid annular blank and cutting helical slots in the periphery of saidblank, said slots being helical with respect to the axis of said ring.

7. Themethod of making a turbine nozzle ring, comprisingundercutting asolid annular blank, cutting helical slots in the periphery of saidblank, said slots being'helical with respect to the axis of saidring,then bending toward said axis that part of the walls of the slotsthatoverhang said undercut portion. I I

8; The method of making a turbine nozzle ring, comprising undercutting asolid annular blank, cutting helical slots in the periphery of saidblank, said slots being helical with respect'to the axis of said ring,then bending toward said axis that part of the walls of the slots thatoverhang said under cut portion, then filling the'said slots with analloy and turning down the side of the 1iilng opposite the undercutportion to a prowith said annular portion, said blades graduallydecreasing in height from one part to the other, and'a diaphragm seatedon this last-mentioned part.

10. A turbine nozzle ring, comprising an annular portion and nozzleblades, helical with respect to the axis of said portion, said 9. Aturbine nozzle ring, comprising an. annular portlon and nozzle bladesintegral blades gradually decreasing in height from one part to theother, and a diaphragm seated on this last-mentioned part.

11. A turbine nozzle ring, comprising an annular portion and nozzleblades, helical with respect to the axis of said portion and integraltherewith, said blades gradually decreasing in height from one part tothe other, and a diaphragm seated on this lastmentioned part.

12. A turbine nozzle ring, comprising an annular portion, bladesdefining nozzles on one part of said ring, said annular portion servingas supportin means for supporting the nozzle ring, said blades graduallydecreasing in height from one part to the other, and a diaphragm seatedon this last mentioned part.

13. The combination as claimed in claim 12, the mentioned parts beingmade integral.

1%. A turbine nozzle ring, comprising an annular portion, bladesintegral therewith defining slots helical with respect to the axis ofsaid annular portion, located toward one end of the annular portion, theother end of said annular portion being adapted to be supported on theturbine casing.

15. A turbine nozzle ring, comprising an annular portion, nozzle bladesdefining slots helical with respect to the axis of saidannular portion,said nozzle blades being undercut at one side.

16. A turbine nozzle ring, comprising an annular portion, nozzle bladesdefining slots helical with respect to the axis of said annular portion,said nozzle blades being undercut at one side, said blades, adjacentsaid undercut portion, being curved toward the said axis,

17. The combination as claimed in claim 15, the mentioned parts beingintegral with one another.

18. The combination as claimed in claim 16, the mentioned parts beingintegral with one another.

19. A turbine nozzle ring, comprising an annular portion, bladesdefining slots helical with respect to the axis of said annular portion,the said blades each decreasing gradually in height from one part to theother, whereby the slots are caused to decrease in cross-sectional areafrom one part to another.

20. In combination with a turbine, a casing, a diaphragm arranged todivide the casing into inlet and exhaust chambers, a nozzle ring cutaway at its outer edge and means to hold said diaphragm in engagementwith the cut away portion of said nozzle ring.

21. In combination with a turbine, a casing, a diaphragm arranged todivide the casing into inlet and exhaust chambers, a nozzle ring, saiddiaphragm being arranged to engage with said nozzle ring and means toattach said nozzle ring to the casing.

In testlmony whereof I aflix my signature.

EARL H. SHERBONDY.

Copies of this patent may be obtained for five cents each, by addressingthe Commissioner of Patents, Washington, D. 0.

